This document reports the results of a 12-month contract to evaluate candidate refractory and insulator materials for use as the inlet duct liner, rotor, and nozzle exit, of a hot gas thrust vector control system. The purpose of this investigation was to define materials that would provide a minimum weight valve design. Materials were compared for erosion resistance when subjected to the particle-laden hot gas environment from a solid propellant motor firing approximating that expected in an advanced interceptor control system application. The best materials selected through design, analysis and test were chemically vapor deposited tungsten for the valve rotor and nozzle and rubber modified silica phenolic for the inlet duct liner. (Author)

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